Lunar Flashlight

Leaping CubeSats! Enabling Beyond-Earth Missions in Small, Inexpensive Packages

CubeSat Developers Spring Workshop; CalPoly-San Luis Obispo

2016 April 21 Robert L. Staehle, Instruments Division Copyright ©2016 California Institute of Technology. Technology. Copyright ©2016 California Institute of U.S. Government acknowledged.sponsorship XI-IV “sai-four”/Univ. of Tokyo, launched MarCO/JPL, 2015/12/6

2003/6/30 news/img/011231l.jpg http://www.space.t.u-tokyo.ac.jp/cubesat/ Starting Small: moving out into the Solar System

1999 CubeSats conceived 2003 First CubeSats in orbit (Wikipedia definition) 2010./11 GAINSTAM Workshop 2010 end 70 total CubeSats launched to date (modified St. Louis Univ. count*) 2010./4, 9 NIAC proposal submitted, funded 2011./7 Interplanetary CubeSat capabilities briefed to AES/HEOMD 2012/9 NIAC Interplanetary CubeSat report 2012/11 INSPIRE funded 2013/9 HEOMD funds BioSentinel, Lunar Flashlight, Near-Earth Asteroid Scout 2014/6 INSPIRE complete, stored for launch 2015/12 MarCO complete 2015 end 428 total CubeSats launched to date (modified St. Louis Univ.Acronyms: count*) GAINSTAM = Government and Industry Nano-Satellite Technology and Mission, hosted at Boeing, Huntington Beach 2010/11/3. NIAC = NASA Innovative Advanced Concepts INSPIRE = Interplanetary NanoSpacecraft Pathfinder In a Relevant Environment HEOMD = Human Exploration & Operations Mission Directorate (NASA HQ) MarCO = Mars CubeSat One *excludes 7 “CubeSats” launched before 2003, from https://sites.google.com/a/slu.edu/swartwout/home/cubesat-database CubeSat Workshop 2011 August 6-7 Interplanetary CubeSats: Logan, Utah Opening the Solar System to a Broad Community at Lower Cost Robert Staehle* Diana Blaney Hamid Hemmati Martin Lo Pantazis Mouroulis Paula J. Pingree Thor Wilson Jet Propulsion Laboratory/ California Institute of Technology

Valles Marineris Jordi Puig-Suari Austin Williams CalPoly San Luis Obispo

Bruce Betts Louis Friedman The Planetary Society

Tomas Svitek Stellar Exploration

6U Total (10 X 20 X 30 cm) ^ 2U Miniature Imaging Spectrometer visible/near-IR, Δλ= 10 nm based on instruments currently being built at JPL

2U Solar sail: >6 X 6 m square ! 5 m/sec/day @ 1 AU solar distance based on Planetary Society/Stellar Exploration LightSail 1

1U Optical telecom flight terminal: 1 kbps @ 2 AU Earth-s/c distance NIR transmitting to existing facility based on JPL Laser Telecommunications development

1U Satellite housekeeping (C&DH, power, attitude determination & stabilization) based on CalPoly CP7 and JPL/Univ of Michigan COVE

Pre-decisional – for planning and discussion purposes only Six Technology Challenges

1. Interplanetary Getting to environment Interplanetary CubeSats Taxonomy

• Launch off C3>0 ~ballistic traj – Cruiser • Depart from “Mothership”, 10s to 100s m/sec 2. Telecommunications – Companion – Orbiter – Lander – Impactor 6. Maximizing downlink info content • Self-propelled 3. Propulsion 1 – 10 km/sec/yr (where needed) 5.Instruments – Electric – Solar Sail

4. Navigation 5 5 Pre-decisional – for planning and discussion purposes only NIAC Results (our forecast)… “Investigation during our Phase 1 work has demonstrated the feasibility of a new class of missions that can open Solar System exploration to a broader community of participants at lower cost. Looking ahead to the 2020s, the work proposed here will enable missions that depart Earth’s vicinity several times a year—at one-tenth the cost of current Discovery missions—to a variety of destinations with focused goals of small body science, lunar and planetary investigations, space physics, heliophysics, and technology development. Interplanetary CubeSat missions will be mounted by NASA Centers, well-equipped universities, and small businesses in ways that were simply unattainable when mission costs were measured in multiples of $100M.”

• New architecture ! new mission class ! broader community involvement • Missions leave Earth a few times a year • Focused objectives (<

Pre-decisional – for planning and discussion purposes only Example Missions

A. Mineral Mapping of Asteroids [Small Body Science]

B. Solar System Escape [Tech Demo]

C. Earth-Sun System [Space- and Helio-physics] e.g., Sub-L1 Space Weather Monitor

D. Phobos Sample Return [Solar System Science]

E. Earth-Moon L2 Radio-Quiet Observatory [Astrophysics]

F. Out-of-Ecliptic [Space Physics, Heliophysics]

7 Pre-decisional – for planning and discussion purposes only 2012 Concept looks crude today…

From: Robert L. Staehle, Brian Anderson, Bruce Betts, Diana Blaney, Channing Chow, Louis Friedman, Hamid Hemmati, Dayton Jones, Andrew Klesh, Paulett Liewer, Joseph Lazio, Martin Wen-Yu Lo, Pantazis Mouroulis, Neil Murphy, Paula J. Pingree, Jordi Puig-Suari, Tomas Svitek, Austin Williams, Thor Wilson, “Interplanetary CubeSat Architecture and Missions”, AIAA Space2012, Pasadena, CA 2012 September 12 A Fractionated Space Weather Base at L5 Using Solar Sails and CubeSats Concept originated at Small Satellites: A Revolution in Space Science Workshop, 2012 July & October, Sponsored by Keck Institute of Space Studies (KISS) at Caltech, Pasadena, California.

From: Paulett C. Liewer, Brian D. Anderson, Vassilis Angelopoulos, Manan Arya, James W. Cutler, Andrew T. Klesh, E. Glenn Lightsey, Martin

W. Lo, Neil Murphy, Sergio Pellegrino, Robert L. Staehle and Angelos Vourlidas, “A Fractionated Space Weather Base at L5 Using Solar Sails and CubeSats,” Poster for American Astronomical Soc. 44th Solar Physics Division Meeting, Bozeman, Montana, 2013 July 8-11 Pre-decisional – for planning and discussion purposes only Far-out concept: Can two Interplanetary CubeSats retrieve a sample from Phobos or Deimos?

Robert Staehle, Louis Friedman 2012 May 10 Art: Ryan Sellers/CalPoly SLO Pre-decisional – for planning and discussion purposes only 5.Instruments

Lens/immersion medium Overview The spectrometer is a miniaturized version of the compact Dyson design form that is currently under development at JPL and elsewhere. Our work will extend our concept from the PRISM airborne spectrometer, tested in early 2012, and a fast, wide-field imaging spectrometer demonstrated as a laboratory breadboard through NASA’s PIDDP program. Detector Instrument Electronics • Detector similar to the one flown on PRISM (Portable Remote Imaging Spectrometer) • Data processing based on a heritage design • Consumes ~1W of average power • Detector interface and data storage would be a new design feature Pantazis Mouroulis 2011 11 Pre-decisional – for planning and discussion purposes only Among the instruments that have come to or are approaching fruition at CubeSat size… • Imaging spectrometer (shown; Blaney, Mouroulis, et al.) • Magnetometer • Microwave radiometer • Radar • pick your favorite…

(2012), Presentation 1105.pdf (2012), Presentation

12 D. L. Blaney, P. Mouroulis, B. Van Gorp R. Green, J. Mouroulis, B. Van P. D. L. Blaney, “The Gorp, and D. Wilson., B. Van G. Sellar, Rodriguez, Ultra Compact Imaging Spectrometer (UCIS),” for Instrumentation on Workshop International Missions Planetary Design Overview

CubeSat Overview: X-Band Patch Antennas (JPL) Volume: 3U UHF Antenna [two sets] (10x10x30cm) (ISIS) Mass: 4.05 kg

Power Generation: Magnetometer (JPL/ UCLA) 3 Axis Stabilized: 21 W Tumbling: 13.7 W Data Rate: 62-260000 Cold-Gas ACS (U. Texas) bps Star Tracker (Blue Canyon) Software: Developed in-house (protos) I&T: In-house S/C I&T, external C&DH + Watchdog Board + environmental testing, NASA Processing Board Lithium UHF (AstroDev) CLI P-Pod/Launch (CalPoly / Tyvak) Integration Operations: Primary: DSN S/CSecondary components (Receive provide only): the Deployable Solar Panels + DSS-28basis for (GAVRT), future high- & Structure Secondarycapability, lower-cost-riskStations, ex: (Pumpkin) Peachmissions Mountain beyond Earth Nav/Comm X-Band Radio (JPL) expanding and provide NASA leadership in an emergent Electrical Power System + domain Battery Board (U. Michigan) Interplanetary NanoSpacecraft Pathfinder In a Relevant Environment

INSPIRE Flight Spacecraft from: Andrew Klesh, Lauren Halatek, et al., INSPIRE: Interplanetary NanoSpacecraft Pathfinder In a Relevant Environment, International Astronautical Congress, Toronto, Canada 2014 October. Completed On-Cost / On-Schedule Multiplying Mars Lander Opportunities with MARSDROP Microlander 2015 June 11 IAA Low Cost Planetary Missions Conference Berlin, Germany

Robert L. Staehle/Jet Propulsion Laboratory-California Institute of Technology Matthew A. Eby/Aerospace Corp., Rebecca M. E. Williams/Planetary Science Institute Copyright 2015. Allrights reserved. Copyright2015. Sara Spangelo, Kim Aaron, Rohit Bhartia, Justin Boland, Lance Christensen, Siamak Forouhar, Marc Lane, Manuel de la Torre Juarez, Nikolas Trawny, Chris Webster/JPL-Caltech David Paige/University of California-Los Angeles

NASA Graph: Technical Note D-5965 Design Sizing Point • L/D = 3, CR=1.00 • Produces a 70° Glide Angle Pre-decisional – for planning and discussion purposes only Master Equipment List Suppliers shown only for proof-of-concept; no selection is represented. Subsystem Components Mass Power Heritage / Supplier

Entry & Descent Aeroshield (1,200 g), Parawing (400 g), 1,620 g - REBR/Aerospace Corp. Stepper motors (2 x 10 g) Payload Methane Detector (Tunable Laser Spectrom-TLS) 100 g 0.67 W MSL/ JPL Pressure, Air Temperature, and Humidity Sensors 113 g 0.43 W MSL/ JPL, various Payload/Navigation Descent/Geology Camera (2 x 40g) 80 g 1 W None*/ Aptina Navigation IMU (Gyro & Accelerometer) 10 g 0.1 W Variable/ Blue Canyon Tech.

Power Body-Mounted Solar Panels (20 x UJT Cells) 40 g - Variable/ Spectrolab Batteries (6x18650 Li Ions, ~16 W-hr each max) 270 g - INSPIRE/ Panasonic Electric Power System & Battery Board 80 g - RAX & INSPIRE/ JPL Computing & Data Gumstix Flight Computer & Storage 10 g 0.5 W IPEX/ Gumstix Handling Telecom UHF Proxy-1 Radio 50 g 2 W Variable/ JPL UHF Low Gain Antenna (Whip) 5 g - Variable/ JPL Mechanical & Others Shelf (68 g), Brackets (26 g), Wing Actuator (19 256 g - Variable/ JPL g), Springs (48 g), Hinges (7 g), Fasteners (20 g), Harnessing (50 g), and others (20 g) Thermal Heaters (3 x 50 g), Aerogel (10 g) 160 g 2 W Variable/ JPL Sterilization Sterilization Bag 100 g - Variable/ JPL TOTAL Total No Margin/ With 20% Margin 2.9 kg/ ~3 W - Pre-DecisionalInformationPlanning For -- and Discussion Purposes Only *Radiation3.5 kg (~3.5 krad)(avg) and thermal testing will be performed to ensure reliability Entry mass (3.5 kg) consistent w/ mass from Aerospace Corp. REBR flights from Earth orbit. Note: the Backpack (ACS & mechanical interfaces, spring for jettison) is an additional 0.7 kg/ 0.9 kg (30% margin). Jet Propulsion Laboratory California Institute of Technology

Mars 2020 Project

18 MarsDrop: Out-of-form-factor Mars MicroLander could be enabled by CubeSat/smallsat thinking, cost approach, and componentry.

Artist’s concept of the JPL/Aerospace/PSI jointly developed MarsDrop concept (Image courtesy of and reprinted by permission of The Aerospace Corporation). Pre-decisional – for planning and discussion purposes only First Interplanetary CubeSat Session, at the 13th Annual CubeSat Developer’s Workshop

MarCO – Ready for Launch Andrew Klesh, et al., JPL

BioSentinel: Mission Development of a Radiation Biosensor to Gauge DNA Damage and Repair Beyond Low Earth Orbit on a 6U Nanosatellite Matthew D'Ortenzio, NASA Ames

Payload Developments on the Lunar Flashlight Mission Travis Imken, et al., JPL

Lunar Ice Cube: Lunar Water Dynamics via a First Generation Deep Space CubeSat Pamela E. Clark, et al., JPL, Morehead State Univ., NASA/GSFC, Busek, Vermont Technical College

The Lunar Polar Hydrogen Mapper (LunaH-Map) CubeSat Mission Craig Hardgrove, et al., ASU, and others

A 6U CubeSat Designed for Lunar Orbit and Beyond in the NASA CubeQuest Challenge Kathleen Morse, Yosemite Space, Inc.

DustCube, a 3U Cubesat to Characterize the natural dust environment and microscopic ejecta due to DART high speed impact on the Binary asteroid 65803 Didymos Diego Nodar, et al., Universitario de Vigo (Spain)

The CuSP interplanetary CubeSat mission Don George, et al., SwRI, JPL, NASA/GSFC

Architectural Flexibility of the Iris Deep-Space Transponder Masatoshi M. Kobayashi, et al., JPL Backup information. 6 New Technologies ! 1 New Architecture CubeSat electronics and subsystems • extended to operate in the interplanetary environment • radiation and duration of operation

Optical telecommunications • very small, low power uplink/downlink over 2 AU distances [rf also discussed] Solar sail propulsion • rendezvous with multiple targets using no propellant [other propulsion techniques also discussed] Navigation of the Interplanetary Superhighway • multiple destinations over reasonable mission durations • achievable ΔV

Small, highly capable instrumentation • (miniature imaging spectrometer example) • acquire high-quality scientific and exploration information

Onboard storage and processing • maximum utility of uplink and downlink telecom capacity • minimal operations staffing